AG12 (ag12-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG12 (ag12-il) Reynolds number: 50,000 Max Cl/Cd: 35.12 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag12-il-50000-n5.txt Download as CSV file: xf-ag12-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5495 0.09888 0.09212 0.0078 1.0000 0.0462
-7.750 -0.5452 0.09474 0.08804 0.0057 1.0000 0.0444
-7.500 -0.5410 0.09030 0.08367 0.0025 1.0000 0.0427
-7.000 -0.5201 0.07597 0.06930 -0.0167 1.0000 0.0373
-6.750 -0.5081 0.07076 0.06406 -0.0204 1.0000 0.0370
-6.500 -0.4937 0.06506 0.05824 -0.0253 1.0000 0.0370
-6.250 -0.4770 0.05918 0.05215 -0.0304 1.0000 0.0372
-6.000 -0.4600 0.05366 0.04642 -0.0344 1.0000 0.0380
-5.750 -0.4426 0.05070 0.04345 -0.0353 1.0000 0.0404
-5.500 -0.4198 0.04556 0.03791 -0.0388 1.0000 0.0409
-5.250 -0.3946 0.04049 0.03230 -0.0416 1.0000 0.0409
-5.000 -0.3682 0.03619 0.02742 -0.0433 1.0000 0.0414
-4.750 -0.3410 0.03257 0.02323 -0.0443 1.0000 0.0426
-4.500 -0.3133 0.02950 0.01960 -0.0446 1.0000 0.0448
-4.250 -0.2852 0.02708 0.01656 -0.0446 1.0000 0.0505
-4.000 -0.2592 0.02514 0.01442 -0.0444 1.0000 0.0570
-3.750 -0.2320 0.02318 0.01209 -0.0436 1.0000 0.0633
-3.500 -0.2060 0.02176 0.01066 -0.0434 1.0000 0.0797
-3.250 -0.1793 0.02032 0.00907 -0.0428 1.0000 0.1019
-3.000 -0.1520 0.01894 0.00789 -0.0429 1.0000 0.1502
-2.750 -0.1250 0.01769 0.00708 -0.0431 1.0000 0.2445
-2.500 -0.0996 0.01674 0.00658 -0.0428 1.0000 0.3654
-2.250 -0.0759 0.01597 0.00617 -0.0418 1.0000 0.4853
-2.000 -0.0550 0.01520 0.00582 -0.0398 1.0000 0.6071
-1.750 -0.0383 0.01428 0.00546 -0.0361 1.0000 0.7727
-1.500 -0.0058 0.01380 0.00490 -0.0366 1.0000 1.0000
-1.250 0.0209 0.01381 0.00454 -0.0366 1.0000 1.0000
-1.000 0.0470 0.01384 0.00430 -0.0365 1.0000 1.0000
-0.750 0.0727 0.01389 0.00414 -0.0363 1.0000 1.0000
-0.500 0.0982 0.01396 0.00405 -0.0362 1.0000 1.0000
-0.250 0.1233 0.01406 0.00401 -0.0360 1.0000 1.0000
0.000 0.1482 0.01418 0.00401 -0.0358 1.0000 1.0000
0.250 0.1728 0.01434 0.00410 -0.0356 1.0000 1.0000
0.500 0.1969 0.01455 0.00426 -0.0355 1.0000 1.0000
0.750 0.2256 0.01480 0.00450 -0.0365 0.9952 1.0000
1.000 0.2769 0.01505 0.00474 -0.0415 0.9682 1.0000
1.250 0.3241 0.01523 0.00494 -0.0453 0.9373 1.0000
1.500 0.3676 0.01536 0.00512 -0.0481 0.9032 1.0000
1.750 0.4066 0.01550 0.00532 -0.0497 0.8656 1.0000
2.000 0.4405 0.01565 0.00547 -0.0500 0.8259 1.0000
2.250 0.4698 0.01586 0.00563 -0.0492 0.7846 1.0000
2.500 0.4962 0.01611 0.00581 -0.0480 0.7429 1.0000
2.750 0.5212 0.01641 0.00603 -0.0465 0.7011 1.0000
3.000 0.5456 0.01676 0.00636 -0.0450 0.6595 1.0000
3.250 0.5699 0.01715 0.00666 -0.0435 0.6182 1.0000
3.500 0.5941 0.01758 0.00701 -0.0422 0.5771 1.0000
3.750 0.6183 0.01805 0.00740 -0.0410 0.5363 1.0000
4.000 0.6425 0.01856 0.00784 -0.0399 0.4958 1.0000
4.250 0.6668 0.01911 0.00842 -0.0389 0.4553 1.0000
4.500 0.6909 0.01971 0.00897 -0.0380 0.4151 1.0000
4.750 0.7153 0.02037 0.00959 -0.0372 0.3749 1.0000
5.000 0.7398 0.02109 0.01028 -0.0366 0.3350 1.0000
5.250 0.7639 0.02189 0.01104 -0.0360 0.2958 1.0000
5.500 0.7879 0.02278 0.01202 -0.0354 0.2573 1.0000
5.750 0.8115 0.02378 0.01303 -0.0348 0.2213 1.0000
6.000 0.8346 0.02492 0.01415 -0.0342 0.1890 1.0000
6.250 0.8573 0.02619 0.01540 -0.0336 0.1593 1.0000
6.500 0.8794 0.02763 0.01686 -0.0330 0.1339 1.0000
6.750 0.9017 0.02925 0.01864 -0.0322 0.1118 1.0000
7.000 0.9225 0.03099 0.02045 -0.0315 0.0941 1.0000
7.250 0.9437 0.03302 0.02270 -0.0307 0.0796 1.0000
7.500 0.9636 0.03523 0.02499 -0.0298 0.0686 1.0000
7.750 0.9833 0.03747 0.02764 -0.0290 0.0582 1.0000
8.000 1.0020 0.04088 0.03147 -0.0279 0.0532 1.0000
8.250 1.0183 0.04380 0.03480 -0.0272 0.0472 1.0000
8.500 1.0310 0.04711 0.03843 -0.0265 0.0427 1.0000
8.750 1.0393 0.05184 0.04384 -0.0258 0.0405 1.0000
9.000 1.0419 0.05689 0.04945 -0.0255 0.0393 1.0000
9.250 1.0385 0.06219 0.05520 -0.0256 0.0386 1.0000
9.500 1.0284 0.06775 0.06113 -0.0264 0.0383 1.0000
9.750 1.0112 0.07349 0.06713 -0.0282 0.0385 1.0000
10.000 0.9901 0.08012 0.07392 -0.0323 0.0392 1.0000
10.250 0.9691 0.08861 0.08249 -0.0394 0.0400 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG12 (ag12-il)